Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV)
Unmanned Aerial Vehicles (UAVs) have been widely used both in military and civil across the world in recent years. Nevertheless, their design always involves complex design optimization variables and decisions. Therefore, this paper aims to guide through the designing, manufacturing, and testing of...
| Main Authors: | , , , , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Elsevier
2023-09-01
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| Series: | Ain Shams Engineering Journal |
| Subjects: | |
| Online Access: | http://www.sciencedirect.com/science/article/pii/S2090447922004051 |
| _version_ | 1797676301097631744 |
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| author | Mohammed El Adawy Elhassan H. Abdelhalim Mohannad Mahmoud Mohamed Ahmed Abo zeid Ibrahim H. Mohamed Mostafa M. Othman Gehad S. ElGamal Yahia H. ElShabasy |
| author_facet | Mohammed El Adawy Elhassan H. Abdelhalim Mohannad Mahmoud Mohamed Ahmed Abo zeid Ibrahim H. Mohamed Mostafa M. Othman Gehad S. ElGamal Yahia H. ElShabasy |
| author_sort | Mohammed El Adawy |
| collection | DOAJ |
| description | Unmanned Aerial Vehicles (UAVs) have been widely used both in military and civil across the world in recent years. Nevertheless, their design always involves complex design optimization variables and decisions. Therefore, this paper aims to guide through the designing, manufacturing, and testing of an electrically powered radio-controlled aircraft for achieving a take-off, cruise, safe landing and carrying the highest payload possible. The whole process involves several phases, design phase, structural analysis, performance analysis, materials used, manufacturing, and finally aircraft testing. The final aircraft was designed with an empty weight and maximum take-off weight of 15.43 Ibs and 33.07 Ibs respectively while the wingspan, cruising speed and maximum speed were 70.1 in., 46 ft/s and 78 ft/sec respectively with a total take-off distance of 100 ft. |
| first_indexed | 2024-03-11T22:27:00Z |
| format | Article |
| id | doaj.art-90e37f58adcc463aa1ad1512754ea122 |
| institution | Directory Open Access Journal |
| issn | 2090-4479 |
| language | English |
| last_indexed | 2024-03-11T22:27:00Z |
| publishDate | 2023-09-01 |
| publisher | Elsevier |
| record_format | Article |
| series | Ain Shams Engineering Journal |
| spelling | doaj.art-90e37f58adcc463aa1ad1512754ea1222023-09-24T05:14:49ZengElsevierAin Shams Engineering Journal2090-44792023-09-01149102094Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV)Mohammed El Adawy0Elhassan H. Abdelhalim1Mohannad Mahmoud2Mohamed Ahmed Abo zeid3Ibrahim H. Mohamed4Mostafa M. Othman5Gehad S. ElGamal6Yahia H. ElShabasy7Corresponding author.; Mechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptMechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptMechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptMechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptMechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptMechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptMechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptMechanical Engineering Department, Faculty of Engineering, Alexandria University, Alex 21544, EgyptUnmanned Aerial Vehicles (UAVs) have been widely used both in military and civil across the world in recent years. Nevertheless, their design always involves complex design optimization variables and decisions. Therefore, this paper aims to guide through the designing, manufacturing, and testing of an electrically powered radio-controlled aircraft for achieving a take-off, cruise, safe landing and carrying the highest payload possible. The whole process involves several phases, design phase, structural analysis, performance analysis, materials used, manufacturing, and finally aircraft testing. The final aircraft was designed with an empty weight and maximum take-off weight of 15.43 Ibs and 33.07 Ibs respectively while the wingspan, cruising speed and maximum speed were 70.1 in., 46 ft/s and 78 ft/sec respectively with a total take-off distance of 100 ft.http://www.sciencedirect.com/science/article/pii/S2090447922004051DesignFabricationUAVWingTailFuselage |
| spellingShingle | Mohammed El Adawy Elhassan H. Abdelhalim Mohannad Mahmoud Mohamed Ahmed Abo zeid Ibrahim H. Mohamed Mostafa M. Othman Gehad S. ElGamal Yahia H. ElShabasy Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV) Ain Shams Engineering Journal Design Fabrication UAV Wing Tail Fuselage |
| title | Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV) |
| title_full | Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV) |
| title_fullStr | Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV) |
| title_full_unstemmed | Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV) |
| title_short | Design and fabrication of a fixed-wing Unmanned Aerial Vehicle (UAV) |
| title_sort | design and fabrication of a fixed wing unmanned aerial vehicle uav |
| topic | Design Fabrication UAV Wing Tail Fuselage |
| url | http://www.sciencedirect.com/science/article/pii/S2090447922004051 |
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